iKarus 61141 Pilot Operating Handbook Download

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Pilot Operating Handbook for the C42 Series

POH C42 SERIES ISSUE1 (B) REV7 25/04/2020

Page 45 of 73

12.3

Cruise Speed (Single Seated)

Rotax 912 UL

Rotax 912 UL S

C42 à 4700 trs/min (65%)

155 km/h (84 kts)

165 km/h (89 kts)

C42B à 4700 trs/min (65%)

160 km/h (86 kts)

170 km/h (92 kts)

C42C à 4700 trs/min (65%)

165 km/h (89 kts)

175 km/h (94 kts)

C42CS à 4700 trs/min (65%)

175 km/h (94 kts)

185 km/h (99 kts)

Speed for a maximum range:

140 km/h (76 kts)

145 km/h (78 kts)

Maximum range with a 50l tank with no wind :

approx. 270 nm (500 km)

Maximum range with a 65l tank with no wind :

approx. 350 nm (650 km)

12.4

Performance with Engine Shut Down

(Single Seated)

Maximal Take-off mass:

472.5 kg

Minimum sink rate:

2 m/s (393 ft/min)

à 85 km/h (46 kts) with flaps in position II

Best glide raio

1 :11

à 95 km/h (51 kts)

ATTENTION :

Follow the instructions in the ROTAX operator’s manual.

Summary of Contents for 61141

Page 1: ...ssue1_v7 Date 25 April 2020 This handbook is to be kept in the aircraft at all times The described options of the C42 Series use are certified for Germany and have been tested in Germany Please note t...

Page 2: ...Adding noise section 23 02 2017 L Chan 2 1 Minor text changes 07 09 2017 L Chan 3 1 Speed modification and text changes 12 09 2017 L Chan 4 1 Change of contact details 23 02 2019 L Chan 5 1 Change of...

Page 3: ...0 7572 3309 Email post comco ikarus de Email info dkl lsa eu Certification Data Information Contact COMCO IKARUS GmbH DKL Light Sport Aircraft Sarl Am Flugplatz 11 6 rue Gaessel D 88367 Hohentengen L...

Page 4: ...an result in serious injury or death Pilots holding licenses for other categories even higher ones are required to be checked out by an appropriately qualified instructor prior to flying this aircraft...

Page 5: ...es would invalidate any certificate of airworthiness or permit to fly and as such would result in an insurance becoming null and void All operating difficulties and equipment failures should be report...

Page 6: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 6 of 73 Three Side Views IKARUS C42 C42A...

Page 7: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 7 of 73 IKARUS C42B...

Page 8: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 8 of 73 IKARUS C42C...

Page 9: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 9 of 73 IKARUS C42CS...

Page 10: ...ap Settings 15 1 9 Maximal Speed for Flap Settings 15 1 10 Propellers for BRP ROTAX 912 UL 16 1 11 H lices pour BRP ROTAX 912 ULS 17 1 12 Noise Table for BRP ROTAX 912 UL and 912 ULS 18 1 12 1 ROTAX 9...

Page 11: ...Maneuver 33 5 2 Suspension 33 5 3 Parking 34 5 4 Tie Down 34 6 Minimum Equipment List 36 7 Dimensions 36 8 Weight and Balance 37 8 1 Empty Weight and Center of Gravity 38 9 Data Placard and Check Lis...

Page 12: ...58 17 1 Equipment 58 17 2 Assembling and Disassembling 58 17 3 Operation 59 18 Flying the C42 Series without Doors 60 19 Instructions for using of LiFe Battery 60 20 COMCO IKARUS Manufacturer Warrant...

Page 13: ...s Maximum maneuver speed VA 148 km h 80 kts Speed with landing flaps set until 2009 Vfe 105 km h 56 kts since 2010 Vfe 117 km h 63 kts Stall speed flap position I VS 75 km h 40 kts flap position II VS...

Page 14: ...il 2009 71 105 km h 38 57 kts since 2010 71 117 km h 38 63 kts Green arc C42 C42A B C 79 180 km h 43 97 kts C42CS 79 187 km h 43 100 kts Yellow arc C42 C42A B C 180 216 km h 97 116 kts C42CS 180 225 k...

Page 15: ...5800 trs min for 5 min max Maximum continuous RPM n 5500 trs min 1 7 RPM Gauge Markings Yellow arc n 5500 5800 rpm Red line n 5800 rpm 1 8 Flap Settings Position I cruising Position II take off landin...

Page 16: ...n 2150 1 min With propeller GSC 3 blade 68 1 72 m Pitch 21 0 400 mm from hub Full throttle RPM on ground max 4900 1 min Propeller RPM approx n 2150 1 min With propeller Neuform CR2 75 2 blade 69 1 75...

Page 17: ...und max 4900 1 min Propeller RPM approx n 2000 1 min With propeller Neuform CR3 V R2H 3 blade 71 1 80 m variable Pitch de 16 30 r 750 mm from hub Full throttle RPM on ground entre 4200 5600 1 min Prop...

Page 18: ...Sport Prop 3 blade 60 0 60 60 0 n a GSC 3 blade 59 27 59 27 59 27 n a Neuform CR2 75 2 blade 59 3 59 3 59 3 59 3 Neuform CR3 75 3 blade 55 8 55 8 55 8 55 8 Kiev Prop BB 263 1800 3 blade 59 1 59 1 59...

Page 19: ...rpm 55 43 hp 4300 rpm 51 hp 4300 rpm Type of oil AERO Shell Sport Plus 4 for other types see operating manual ROTAX Oil Quantity min 2 6 l max 3 05 l Oil temperature min 50 C min 50 C max 140 C max 1...

Page 20: ...category of aircraft 3 Note to Engine Operation The Rotax 912 is a 4 cylinder four stroke horizontally opposed water cooled engine Never move the prop with the ignition MAG switches on Fuel type for...

Page 21: ...oil In the case of the C42B C42C and C42CS only the coolant is cooled by a cooler The coolant and oil systems are connected to one heat exchanger thus the temperatures of both fluids adapt to each ot...

Page 22: ...neutral or nose down position When taking off or landing on bumpy grass strips exercise caution to avoid striking the propeller 4 2 Take off and Climb After completing the before take off checklist Ru...

Page 23: ...ssary to compensate both engine and propeller torque during climbing Whenever possible take off into the wind The maximum demonstrated crosswind component for take off and landing is 30 km h 16 kts No...

Page 24: ...hrottle set for the appropriate rpm for horizontal flight Example Typical cruising set up Rotax 912 UL Rotax 912 ULS Engine RPM 4500 rpm 4500 rpm Air Speed 150 km h 81 kts 160 km h 86 kts Fuel consump...

Page 25: ...this condition the aircraft is fully controllable However lateral altitude corrections must be done mainly with the rudder Example right wing low rudder deflection to the left If the aircraft is stall...

Page 26: ...e best speed to engage the flaps is between 90 and 100 km h 48 and 54 kts On final approach with flap position III keep the speed at about 90 km h 48 kts with the engine at idle The glide angle in fla...

Page 27: ...e ignition When landing in a high vegetation grain or similar reduce speed directly above the vegetation by extending the flaps to position III pull stick fully aft and allow the aircraft to sink into...

Page 28: ...altitude you may attempt to restart the engine check Fuel valve OPEN Magneto switches ON Fuel SUFFICIENT Fuel pump ON 4 8 3 Start the Engine in Flight both magneto switches ON electrical fuel pump ON...

Page 29: ...o closely monitor the oil and cylinder head temperature Attention If the cowl flap is closed the cooling air supply to the radiator will not be sufficient over a longer period i e the oil and cylinder...

Page 30: ...pply rudder opposite to the direction of rotation until the rotation will stop Reduce back pressure on stick Slowly pull aircraft up 4 10 4 Spiral Dive Set aileron and rudder opposite to the direction...

Page 31: ...ng rolling moments If in doubt deploy parachute rescue system 4 10 7 Loss of Rudder Control Controlling flat curves is possible with the ailerons only If possible perform a field landing in a straight...

Page 32: ...te get wet it must be aired and repacked Only by the manufacture The parachute is placed in the fuselage as described in the appendices of this manual There is a time limit on the use of the rocket ca...

Page 33: ...e there is no tow bar applicable at the nose gear you must press down the tail to raise the nose wheel off the ground With the nose wheel clear of ground the aircraft can be simply steered by pivoting...

Page 34: ...ng cold weather when accumulated moisture may freeze the brakes or when brakes are overheated 5 4 Tie Down When parking the aircraft outdoors nose into the wind if possible Set parking brakes or block...

Page 35: ...ot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 35 of 73 Tie down point at the upper front strut area Tie down point between the engine cowling and propeller spin...

Page 36: ...tor true Colour Coding Altimeter with Kolsmann window Compass Tachometer Cooling liquid temperature gauge Oil temperature gauge Oil pressure gauge Fuel gauge Generator charge control Data placard Pilo...

Page 37: ...alance Place the aircraft in a level position on three scales with the stabilizer and elevator leveled The center of gravity is measured in mm behind the reference datum and then calculated as a perce...

Page 38: ...X2 mm G2 G2R kg G2L kg __________ kg G1 __________ kg G total __________ kg xs mm mm xs L It is the pilot s responsibility to respect and verify that the aircraft does not surpasses the maximal take...

Page 39: ...rence point BP at empty weight 280 460 mm Place and Date ______________________________________ Signature __________________________________________ Loading plan weight x lever arm torque Empty weight...

Page 40: ...tiveload factor 4 g Negative load factor 2 g Maximum wind speed for operation Steady wind 22 kts 40 km h Demonstrated cross wind component 16 kts 30 km h Payload Max kg Min 65 kg The pilot operating t...

Page 41: ...fastened 2 Control system free and correct 3 Parachute system unlocked 4 Check fuel level 5 Engine fuel shut off valve OPEN 6 Electric fuel pump ON 7 Choke OFF 8 Carburetor preheating OFF C42B C42C C4...

Page 42: ...und adjustable Neuform 3 blade CR3 75 ground adjustable Kiev Prop 3 blade BB 263 1700 ground adjustable Helix 3 blade H50F 1 75m R SI 12 3 ground adjustable Engine BRP ROTAX 912 ULS Gearbox C 2 43 1 A...

Page 43: ...ufacturer for installation required maintenance and particularly the avoidance of moisture in the parachute pack Should the chute get wet it must be aired and repacked There is a time limit on the use...

Page 44: ...ed at rotation 70 km h 38 kts Speed at 15 m obstacle 90 km h 49 kts Higher elevations and higher temperatures lengthen the take off distances The figures given are valid for a MTOW of 360 kg flown sol...

Page 45: ...94 kts C42CS 4700 trs min 65 175 km h 94 kts 185 km h 99 kts Speed for a maximum range 140 km h 76 kts 145 km h 78 kts Maximum range with a 50l tank with no wind approx 270 nm 500 km Maximum range wi...

Page 46: ...ep 4 Slowly push the wing against fuselage and wing spar brackets Step 5 Before pushing against the spar brackets look for the sideway at the rear spar intake so that to lead the rear wing spar in the...

Page 47: ...t be secured with the ring pins 5 Lift the wing to check that the wing support is fixed tight by the toggle bolt Repeat the step 1 to 6 fo the other wing Remove any aileron locks used Step 7 Attach ri...

Page 48: ...base of the wing support 6 Remove fastening bolts at the rear wing spar 7 Remove fastening bolts at the front wing spar The following 5 steps must be undertaken to fold back the wings Step 1 Lift righ...

Page 49: ...g attachment Check for leakage under the engine cowling Check cooling liquids and lubricants Check secure attachment of the engine cowling Check that coolers are clean oil cooler water cooler Check ai...

Page 50: ...ed properly at the front and rear end of the tubes Check QR Spades of the C42C and C42CS model for secure attachment and deformation 14 4 Left Side of the Fuselage Check condition of glass fiber fairi...

Page 51: ...Wing See 14 3 Left Wing 14 8 Inside and Outside of the Cabin Check condition of windscreen doors including locking mechanism cracks Check free movement of the steering control stick pedals flap lever...

Page 52: ...by the covering specialists When in doubt contact the manufacturer Be especially careful in the maintenance and cleaning of the cabin glazing It is highly recommended to abundantly use clear water wi...

Page 53: ...ons of the C42 COMCO IKARUS GmbH Maintenance Manual and 912 ROTAX Maintenance Manual If not conducted the safety of the aircraft is not guaranteed and warranty claims may be omitted The periodical ins...

Page 54: ...f the wing relative to the main tube 8 5 Note The incidence angle is measured from the lower edge of the rear wing tube to the lower edge of the front wing tube at the root rib b Configuration angle o...

Page 55: ...to rear spar It is defined by the length of the aileron push rods 5 Distance from axis of rotation Aileron Neutral position 7 1 35mm 10mm Upwards 20 2 90mm 10mm Downwards 14 2 70mm 10mm Measuring poin...

Page 56: ...410 mm Flettner rudder C42C C42CS When the elevator neutral Flettner rudder 0 2 78 mm 3 mm Flaps Note Flap angle is measured from the flap bottom to the bottom of the wing at the root area tangent fr...

Page 57: ...Quantity of Oil 200 ml 0 42 pts Hydraulic Oil HVP 10 hydraulique e Brakes In the Ikarus C42 series different brake systems are used e g Sachs Magura Tost and Beringer brakes For service information pl...

Page 58: ...urer The unauthorised alteration of the equipment for handicapped pilots is not permitted 17 2 Assembling and Disassembling The rudder control lever is installed by attaching to the mounted axle in th...

Page 59: ...t LH immediately back to the rudder control lever and steer aircraft during take off run After take off in approximately 5 to 10 m above the runway use LH to check that the throttle lever is still in...

Page 60: ...e set to position III 19 Instructions for using of LiFe Battery The usage of LiFe Batteries on the C42 Series is related to the battery modulation technology which allows for an effective reduction of...

Page 61: ...voltage An automatically disconnection of the charging current is displayed by the charging control lamp To activate the charging circuit again activate the reset button beside the charging control la...

Page 62: ...nience commercial loss lost profits or savings arising out of the use or inability to use the aircraft to the full extent such may be disclaimed by law This warranty does not affect any statutory righ...

Page 63: ...karus Flight Center or Ikarus Service Center in the original configuration as supplied by COMCO IKARUS The microlight aircraft should be accompanied with the following information Name of the owner Ad...

Page 64: ...nal warranty time period The original warranty period will not be extended All original parts that have been replaced shall become the property of Comco Ikarus Comco Ikarus does not warrant the instal...

Page 65: ...mary manner Defects or damage resulting from misuse use with incompatible devices or accessories accident or neglect Defects or damage due to improper operation testing maintenance installation adjust...

Page 66: ...Flaps mechanical Roof rigging Engine oil specifications Inside oil inspection cover Fuel specifications Next to the fuelling cap Baggage loading At the baggage compartment Deviation table Panel Contr...

Page 67: ...production _________________ Never exceed speed C42 180 km h 97 kts C42B C42C 216 km h 116 kts C42CS 225 km h 121 kts Stall speed 65 km h 35 kts Structural limitations positive limit load factor 4 g n...

Page 68: ...l Defect __________________________________ Engine _________________________________________ Airframe _________________________________________ Total Flight Hours Pilot on Aircraft ___________________...

Page 69: ...for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 69 of 73 21 4 Inspections Performed Type ____________ Serial No _________________ Registration ________________________ Date Type of ins...

Page 70: ...IES ISSUE1 B REV7 25 04 2020 Page 70 of 73 21 5 Location of the Parachute Rescue System Important Le collier 450x7 8mmm est a mont autour du collier du fus et de la premi re boucle du sac de parachute...

Page 71: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 71 of 73...

Page 72: ...Pilot Operating Handbook for the C42 Series POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 72 of 73...

Page 73: ...Pilot Operating Handbook for the C42 Series Appendix POH C42 SERIES ISSUE1 B REV7 25 04 2020 Page 73 of 73 21 6 Wiring Diagram...

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